EP0315524B1 - Schubumkehrvorrichtungsgitter für Strahltriebwerke mit einer Düse von veränderbarem Querschnitt - Google Patents

Schubumkehrvorrichtungsgitter für Strahltriebwerke mit einer Düse von veränderbarem Querschnitt Download PDF

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Publication number
EP0315524B1
EP0315524B1 EP88402749A EP88402749A EP0315524B1 EP 0315524 B1 EP0315524 B1 EP 0315524B1 EP 88402749 A EP88402749 A EP 88402749A EP 88402749 A EP88402749 A EP 88402749A EP 0315524 B1 EP0315524 B1 EP 0315524B1
Authority
EP
European Patent Office
Prior art keywords
cowling
downstream
thrust reverser
upstream part
thrust
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP88402749A
Other languages
English (en)
French (fr)
Other versions
EP0315524A1 (de
Inventor
Jacques Marie Gilbert Barbarin
Pascal Bruno Georges Lecoutre
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Transmission Systems SAS
Original Assignee
Hispano Suiza SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hispano Suiza SA filed Critical Hispano Suiza SA
Publication of EP0315524A1 publication Critical patent/EP0315524A1/de
Application granted granted Critical
Publication of EP0315524B1 publication Critical patent/EP0315524B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud

Definitions

  • the present invention relates to a thrust reverser of the secondary flow of a turbofan in which the cowl, forming, during operation of the turbojet in direct thrust, the downstream end of the outer wall of the annular channel of circulation of the vein secondary flow, is capable of being moved axially in the downstream direction by means of a control system comprising for example jacks fixed on the fixed upstream part of the reverser and a displacement of the cowling downstream causes the pivoting of '' a plurality of flaps which obstruct the channel and divert the flow to form an inverted flow, the guidance of which is obtained by means of a device with grids arranged on the external periphery of said channel and which are discovered after displacement downstream of said channel rollover.
  • the thrust reverser consists of two parts, each part comprising a semi-cylindrical part of said downstream cowling whose displacement means comprise for example two jacks and the pivoting said flaps is guided for example by connecting rods to a fixed link articulation point located on the internal wall of said secondary channel.
  • US-A-3779010 describes a thrust reverser of the type with grids and with sliding cover and pivoting flaps in which a partial sliding in the downstream direction of all the movable elements is capable of clearing a passage between the upstream ends upstream fixed part and movable part, thus modifying the nozzle section.
  • FR-A-2184021 describes a nozzle with variable passage section and sliding cowling with two annular parts, associated with a fan with variable pitch and pitch reversal.
  • GB-A-2189550 describes a turbomachine comprising flow control means comprising a movable cowling which in a first position clears a passage on the rear edge of an upstream fixed part so as to increase the outlet section and in a second position causes reversing flaps and releases a passage of the reverse flow in which are placed translatable movable grids.
  • the object of the invention is to provide an improved solution in the production of a thrust reverser which has satisfactory results in all the required operating conditions and in particular by allowing adaptation of the nozzle section to these conditions.
  • each movable downstream half-cowling of the reverser comprises two parts capable of being connected by latch means, an upstream mobile cowling part capable of being connected by a lock at the upstream fixed part of the reverser and a downstream movable cowling part capable of being moved by means of at least one jack in an axial direction downstream, either by driving the upstream part locked on said downstream part and released from its locking on the upstream fixed part, ie independently of the upstream part after release of their mutual lock, the upstream part remaining locked on the upstream fixed part so as, as the case may be, to hide the gates of the inverter in a direct thrust operation corresponding to a phase of cruise flight of the aircraft or to uncover the inversion grids in a thrust inversion operation or to leave the inversion grids masked while providing an increase in the exit section secondary ejection nozzle corresponding to operation of the turbojet engine at full power, by means of a clear passage downstream of the reversing grids.
  • the thrust reverser according to the invention shown in Figures 1 and 1a comprises a fixed structure 1 and a movable structure 2.
  • the fixed structure 1 comprises a front frame 3 having the annular assembly 4 for connecting in the upstream turbojet engine, an internal peripheral box 5 forming a deflection edge 6 and an external peripheral box 7 whose external shape adapts to the shape of the nacelle.
  • On the front frame are fixed the actuators 8 for operating the mobile structure 2, for example two in number per half-assembly.
  • the fixed structure 1 also includes a primary cover 9 and deflection grids 10. Said primary cover 9 forms the internal wall delimiting the secondary stream and on the primary cover 9 are fittings 11 for connecting rods.
  • the deflection grids 10 form an annular peripheral assembly and they have profiles of different shapes, the orientation of which is optimally adjusted from front to back in order to obtain the reversal performance by ensuring optimal guidance of the reverse flow.
  • the fixed structure 1 is further arranged to receive the support pylons of the thrust reverser, in a manner known per se and it also carries the various fixing and guiding elements of the mobile structure 2 of the reverser, in particular hinges 12 of articulation of the movable half-cowlings and of the slides 13 of axial translation arranged in the upper part and in the lower part.
  • the mobile structure 2 like the fixed structure 1, consists of two half-assemblies so that the thrust reverser forms an annular channel in the form of two joined Cs and each half-assembly comprises an external half-cowling 14, movable in axial translation on which is fixed an annular half-set of pivoting flaps 15.
  • Each movable flap 15 is connected by a connecting rod 16 to the fitting 11 of articulation of the primary cover 9 and it pivots around the articulation 17 for fixing on the movable structure, arranged at the front.
  • the cowling 14 carries a rail 18 which cooperates with the slide 13 of the fixed structure 1, in which it slides, according to an embodiment which is for example described in detail by EP-A 0055163.
  • each half-cowling 14 has two parts, respectively upstream 19 and downstream 20.
  • the half-cowling 14 comprises locking means arranged in two places, respectively upstream where the lock 21 ensures the blocking of the half-cowling 14 movable in position retracted on the fixed structure 1 and between the two upstream 19 and downstream 20 parts, where the lock 22 provides mutual locking joining the two said upstream 19 and downstream 20 parts.
  • Said locking means 21 and 22 are made up of cooperating elements respectively integral with each part and are of a known and commonly used type such as claw or hook lock and are associated with any known type of control, hydraulic, electric or pneuma tick, subject to the general control system of the thrust reverser, also of a known type and which does not need to be described in more detail to allow production by a person skilled in the art generally informed of the techniques concerned.
  • the movable external cover 14 is locked in this case by the lock 21 on the fixed structure 1 of the reverser and the downstream part 20 is locked by the lock 22 on the upstream part 19 of the mobile cover 14.
  • the respective external surfaces of the box external 7 of the front frame 3 of the fixed structure 1 of the reverser and the movable external cowling 14 also form a continuous aerodynamic wall delimiting the external flow.
  • the upstream part 19 of the movable cowling 14 is again locked by the latch 21 on the fixed structure 1 of the reverser and consequently, the pivoting flaps 15 are in the retracted position controlled by the position of their front articulation 17 on said upstream part 19.
  • the deflection grids 10 also remain masked by said upstream part 19.
  • the latch 22 is released, thus separating the downstream and upstream parts 19 and 19 of the external cowling 14.
  • the jacks 8 control a limited movement of the only downstream part 20 in axial translation always along the slides 13 and rails 18, in a downstream direction, thus freeing a passage 26 between said downstream parts 20 and upstream part 19.
  • Part of the secondary flow circulating in the secondary channel is then ejected by said passage 26, which is symbolized in FIG. 3 by the arrow 27.
  • said passage 26 which is symbolized in FIG. 3 by the arrow 27.
  • the external surface of the cowling does not has no opening that would generate aerodynamic losses.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)

Claims (1)

1. Schubumkehrvorrichtung für ein Zweistrahl-Turboluftstrahltriebwerk, bestehend aus zwei einen C-förmigen Ringkanal begrenzenden Aggregaten, die jeweils umfassen: eine mit Hilfe von Zylinder-Kolbenanordnungen (8) in axialer Richtung verschiebbare äußere Halbhaube (14), die eine Gruppe von Klappen (15) trägt, die in ausgestellter Position den in dem genannten Kanal zirkulierenden Sekundärkreis umlenken und sich in eingezogener Position derart in die Halbhaube einfügen können, daß sie bei direktem Schub eine kontinuierliche aerodynamische Begrenzungsfläche für die Strömung des Sekundärkreises bilden, ferner eine feste Konstruktionsgruppe, die eine ringförmige Reihe von Umlenkgittern (10) trägt, die in ausgefahrener Position der Schubumkehrvorrichtung, in der sie durch die Verschiebung der äußeren beweglichen Halbhaube freigelegt werden, zur Führung des invertierten Strahls dienen, sowie eine ringförmige Baugruppe (4), die zur Verbindung mit Turboluftstrahltriebwerk dient, dadurch gekennzeichnet, daß jede der stromabwärtigen beweglichen Halbhauben (14) zwei durch Verriegelungsmittel (22) verbindbare Teile (19, 20) aufweist, nämlich einen beweglichen stromaufwärtigen Haubenteil (19), der durch einen Riegel (21) mit dem festen stromaufwärtigen Teil (1) der Schubumkehrvorrichtung verbindbar ist, und einen beweglichen stromabwärtigen Haubenteil (20) der mit Hilfe wenigstens einer Zylinder-Kolbenanordnung (8) entweder durch Antreiben des an dem stromabwärtigen Teil (20) verriegelten und von seiner Verriegelung (21) an dem festen stromaufwärtigen Teil (1) gelösten stromaufwärtigen Teils (19) oder, nach dem Lösen der gegenseitigen Verriegelung (22), unabhängig von dem stromaufwärtigen Teil (19) in stromabwärtiger Richtung axial verschiebbar ist, wobei der stromaufwärtige Teil (19) an dem stromaufwärtigen festen Teil (1) verriegelt bleibt, so daß je nach Lage des Falls die Gitter (10) der Schubumkehrvorrichtung in einer Betriebsart mit direktem Schub, der einer Reiseflugphase des Flugzeugs entspricht, abgedeckt sind, oder in einem Betrieb mit Schubumkehr die Schubumkehrgitter (10) freigegeben werden, oder die Schubumkehrgitter (10) abgedeckt gelassen werden, wobei durch Freilegen eines Durchgangs (26) stromabwärts der Schubumkehrgitter (10) eine Vergrößerung des Austrittsquerschnitts der sekundären Auswurfdüse herbeigeführt wird, die einem Betrieb des Strahltriebwerks mit voller Leistung entspricht.
EP88402749A 1987-11-05 1988-11-03 Schubumkehrvorrichtungsgitter für Strahltriebwerke mit einer Düse von veränderbarem Querschnitt Expired - Lifetime EP0315524B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8715336A FR2622929A1 (fr) 1987-11-05 1987-11-05 Inverseur de poussee de turboreacteur a grilles,a section variable d'ejection
FR8715336 1987-11-05

Publications (2)

Publication Number Publication Date
EP0315524A1 EP0315524A1 (de) 1989-05-10
EP0315524B1 true EP0315524B1 (de) 1991-11-06

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP88402749A Expired - Lifetime EP0315524B1 (de) 1987-11-05 1988-11-03 Schubumkehrvorrichtungsgitter für Strahltriebwerke mit einer Düse von veränderbarem Querschnitt

Country Status (6)

Country Link
US (1) US4922713A (de)
EP (1) EP0315524B1 (de)
DE (1) DE3866084D1 (de)
ES (1) ES2026679T3 (de)
FR (1) FR2622929A1 (de)
GR (1) GR3003681T3 (de)

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Publication number Publication date
GR3003681T3 (de) 1993-03-16
US4922713A (en) 1990-05-08
ES2026679T3 (es) 1992-05-01
EP0315524A1 (de) 1989-05-10
DE3866084D1 (de) 1991-12-12
FR2622929A1 (fr) 1989-05-12

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